Conceptual Design of a Supersonic Jet Engine

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4.3.3.2 HPC A five stage constant outer diameter design was chosen for the MJ – Haran S14. This configuration allows for high hub and mean blade speeds through all stages, which reduces the stage loading. The first stage hub to tip ratio was chosen for an optimal radius of the compressor. Placing it lower would lead to higher pressure losses in the duct following the splitter due to the steep angle, placing it higher would lead to a lower RPM in order to keep 𝑀𝑡𝑖𝑝,𝑟𝑒𝑙 at reasonable values, which in turn could lead to more stages. The final radius is a compromise between these conflicting requirements. To keep the diffusion factor at the tip below 0,4, the reaction has been adjusted to reduce from 0,75 at the first stage towards 0,5 at the last stage. With a 50% reaction the blades are symmetrical 𝛼1 = 𝛽2 = 𝛼3, 𝛽1 = 𝛼2 giving the most efficient diffusion over the stage [19]. However, a 50% reaction was not achievable with five stages. An IGV was implemented to increase the absolute velocity of the first stage, allowing a higher rotational speed while maintaining the same 𝑀𝑡𝑖𝑝,𝑟𝑒𝑙. The HPC component is illustrated in figure 20. Note that the discs are preliminary, the final disc design can be seen in appendix D. Figure 20: HPC component Table 8 shows some key compressor data. Figure 21 shows the velocity triangles at the mean blade and table 9 shows the velocity triangles data at mean blade. A full output of stage by stage performance for the HPC can be found in appendix C. 𝑵𝒖𝒎𝒃𝒆𝒓 𝒐𝒇 𝑺𝒕𝒂𝒈𝒆𝒔 𝑨𝒗𝒈. 𝝍 𝑨𝒗𝒈. ф 𝑨𝒗𝒈. 𝑻𝒆𝒎𝒑 𝒓𝒊𝒔𝒆 𝜼𝒑𝒐𝒍𝒚 𝑴𝒕𝒊𝒑,𝒓𝒆𝒍,𝒊𝒏 𝑹𝑷𝑴/𝑼𝒕𝒊𝒑 5 𝑴𝒂𝒙,𝒊𝒏 0,52 0,58 𝑴𝒂𝒙,𝒐𝒖𝒕 0,33 0,38 𝑨𝑹𝒊𝒏 1,63 89,8𝐾 𝑨𝑹𝒐𝒖𝒕 0,93 0,941 𝑯𝒖𝒃/𝑻𝒊𝒑 − 𝒓𝒂𝒕𝒊𝒐𝒊𝒏 0,70 1,34 𝑬𝑰𝑺 2025 13500/613,8 𝒔/𝒄 − 𝒓𝒂𝒕𝒊𝒐 1,2 𝑰𝑮𝑽 𝒂𝒏𝒈𝒍𝒆 18° 𝑻𝒐𝒕𝒂𝒍 𝒍𝒆𝒏𝒈𝒕𝒉 Table 8: Key HPC data 0,37𝑚 37

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